Prescrizione di Aeronavigabilità

Rif. N.
2014-234 del
07/lug/14
Prescrizione di Aeronavigabilità
Airworthiness Directive
Si allega la Prescrizione di Aeronavigabilità emessa dalla:
Attached the Airworthiness Directive issued by:
Agenzia Europea per la Sicurezza Aerea
European Aviation Safety Agency
Autorità Primaria di Certificazione
Primary Certification Authority
RIFERIMENTO AD
EASA N. 2014-0155
AD Reference
COSTRUTTORE
Manufacturer
CEAPR
SOGGETTO
Applicability
ATL, DR 200, DR 220, DR 221, DR 250, DR 253, DR 300, DR 400,
HR 100, R 1180 and R 3000 aeroplanes
OGGETTO
Subject
Engine - Engine air intake box and air ducting - inspection/
replacement
NOTE
Remark
Cancella le PP.AA. ENAC 1999-160 del 06 aprile 1999 e
1999-462 del 02 dicembre 1999.
Nota 1
Il Certificato di Navigabilità dell'aeromobile sulle cui strutture od impianti deve essere applicata la Prescrizione
di Aeronavigabilità a riferimento, scade di validità qualora essa non venga attuata nei termini prefissati.
The Certificate of Airworthiness of the aircraft to which structures and/or systems the referenced Airworthiness
Directive shall be applied expires if the AD is not embodied within specified terms.
Nota 2
Per ulteriori informazioni contattare ENAC Direzione Regolazione Navigabilità
For further information contact ENAC Airworthiness Regulation Department
email : [email protected]
fax :+390644596611
EASA AD No.: 2014-0155
EASA
AIRWORTHINESS DIRECTIVE
AD No.: 2014-0155
Date: 02 July 2014
Note: This Airworthiness Directive (AD) is issued by EASA, acting in accordance with Regulation
(EC) No 216/2008 on behalf of the European Community, its Member States and of the
European third countries that participate in the activities of EASA under Article 66 of that
Regulation.
This AD is issued in accordance with EU 748/2012, Part 21.A.3B. In accordance with EC 2042/2003 Annex I, Part M.A.301, the
continuing airworthiness of an aircraft shall be ensured by accomplishing any applicable ADs. Consequently, no person may operate an
aircraft to which an AD applies, except in accordance with the requirements of that AD, unless otherwise specified by the Agency [EC
2042/2003 Annex I, Part M.A.303] or agreed with the Authority of the State of Registry [EC 216/2008, Article 14(4) exemption].
Design Approval Holder’s Name:
Type/Model designation(s):
ATL, DR 200, DR 220, DR 221, DR 250, DR 253,
DR 300, DR 400, HR 100, R 1180 and R 3000
aeroplanes
CEAPR
TCDS Numbers:
EASA.A.367, EASA.A.368, EASA.A.372, EASA.A.374, EASA.A.510, EASA.A.551
and EASA.A.552
Foreign AD:
Not applicable
Supersedure:
This AD supersedes DGAC France AD 1999-053 R1 dated 10 March 1999 and
AD 1999-470 dated 01 December 1999.
ATA 73
Engine – Engine Air Intake Box and Air Ducting – Inspection /
Replacement
Manufacturer(s):
Centre est Aéronautique, Avions Pierre Robin, Robin Aviation, Constructions
Aéronautiques de Bourgogne, APEX Industries, Finch Aircraft, Robin Aircraft.
Applicability:
ATL, DR 200, DR 220, DR 221, DR 250, DR 253, DR 300, HR100, R1180 and
R 3000 aeroplanes, all models, all serial numbers (s/n) and
DR 400 aeroplanes, all models, all s/n except those modified in accordance
with EASA STC EASA.A.S.01380 or STC No. 10014219 (TAE 125 diesel
engine installation) .
Reason:
An accident occurred on a DR 400 aeroplane during take-off phase. Technical
investigations showed paint adherence defects inside the engine air intake box,
Part Number 56.15.01.000. It was determined that the engine carburettor had
been blocked by small pieces of paint from the engine air intake box, so that
the engine could not deliver its maximum power and the performance of the
aeroplane, notably during take-off, had been significantly degraded.
This condition, if not detected and corrected, could lead to an engine failure,
possibly resulting in loss of control of the aeroplane.
To initially address this issue, DGAC France published AD 1999-053 (later
revised) to require inspection of the engine air intake box. After that AD was
issued, cohesion defects were found inside the laminated air ducting from
engine filter to engine air intake box. Prompted by these findings, DGAC
France issued AD 1999-470 to require inspection of the engine laminated air
ducting.
TE.CAP.00110-003 © European Aviation Safety Agency. All rights reserved.
Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet.
1/2
EASA AD No.: 2014-0155
Since DGAC France AD 1999-053 R1 and AD 1999-470 were issued, several
engine failures and malfunctions have occurred due to the same root causes.
Consequently, CEAPR issued SB N˚ 161 Revision 3 to provide more detailed
inspection and replacement instructions.
For the reasons described above, this AD retains the requirements of DGAC
France AD 1999-053 R1 and AD 1999-470, which are superseded, and
requires repetitive inspections and, depending on findings, replacement of the
engine air intake box and engine air ducting in accordance with the revised
instructions.
Effective Date:
16 July 2014
Required Action(s)
and Compliance
Time(s):
Required as indicated, unless accomplished previously:
(1) Within 110 flight hours (FH) after the effective date of this AD, and,
thereafter, at intervals not to exceed 110 FH, accomplish a visual and
tactile inspection of the engine air intake box (including the deflection flap)
and the engine air ducting (including the area located downstream of the
filter) in accordance with the instructions of CEAPR SB N°161 Revision 3.
(2) If, during any inspection as required by paragraph (1) of this AD, any
damage such as bubbling, blistering, peeled off areas or paint detachment
is found, before next flight, replace each damaged part with a serviceable
part in accordance with the instructions of CEAPR SB N°161 Revision 3.
(3) Replacement of damaged parts on an aeroplane, as required by paragraph
(2) of this AD, does not constitute terminating action for the repetitive
inspections as required by paragraph (1) of this AD for that aeroplane.
(4) From the effective date of this AD, do not install on any aeroplane a
painted engine air intake box or a repaired engine air ducting.
Ref. Publications:
CEAPR SB N°161 Revision 3 dated 06 September 2012.
The use of later approved revisions of this document is acceptable for
compliance with the requirements of this AD.
Remarks:
1. If requested and appropriately substantiated, EASA can approve
Alternative Methods of Compliance for this AD.
2. This AD was posted on 21 May 2014 as PAD 14-084 for consultation until
18 June 2014. No comments were received during the consultation period.
3. Enquiries regarding this AD should be referred to the Safety Information
Section, Executive Directorate, EASA. E-mail: [email protected].
4. For any question concerning the technical content of the requirements in
this AD, please contact:
CEAPR, Bureau de Navigabilité, 1 Route de Troyes –
21121 DAROIS, FRANCE
Telephone : +33 380 35 25 22, Fax : +33 380 35 25 25
E-mail : [email protected].
TE.CAP.00110-003 © European Aviation Safety Agency. All rights reserved.
Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet.
2/2